Low Cost Propulsion Systems for Launch-, In Space- and SpaceTourism Applications

Transcription

1 Low Cost Propulsion Systems for Launch-, In Space- and SpaceTourism Applications Space Propulsion (Rome, 02 06/05/2016) Dr.-Ing. Peter H. Weuta Dipl.-Ing. Neil Jaschinski WEPA-Technologies GmbH (Germany) Seite Space 1; Propulsion / Rome

2 Introduction: WEPA-Technologies GmbH Seite Space 2; Propulsion / Rome

3 1. Introduction: WEPA-Technologies GmbH Mechanical Engineering, General Automation and Rocket Technology R&D focussed engineering office and manufacturing company - Planning, development and realization of non-standard solutions Manufacturing of prototypes and small lots - company owned 700 m 2 workshop - broad range of manufacturing technologies (CNC- and conventional machining) Seite Space 3; Propulsion / Rome

4 Development Activities Seite Space 4; Propulsion / Rome

5 2. Development Activities (Rocket Technology) Propulsion - Liquid propellant rocket engines (LPRE) - Turbo pumps for LPRE - H 2 O 2 - concentration plants (max. 98 %) - Solid rocket motors (SRM) (Chlorine free) Public references include - CASSIDIAN GmbH (Airbus Defence & Space) - Dynamit Nobel Defence GmbH - EU-customer (H 2 O 2 - concentration plant) CASSIDIAN (now: Airbus Defence & Space) contract development Solid rocket motors (thrust: up to 20 kn) Seite Space 5; Propulsion / Rome

6 Development Strategy: Rocket Technology Seite Space 6; Propulsion / Rome

7 3. Key Development Fields Technology Demonstrator Units LOX / Ethanol (LCH 4, Kerosene, H 2 O 2 ) Turbo Pump 35 kn LPRE Micro Satellite Launch Vehicle; f. ex kg LEO 9 10 to GLOW 3 stage design stage 1: 4 x 35 kn stage 2: 1 x 35 kn Potential customer applications Sounding Rockets H 2 O 2 concentration plants (max. 98 %) H 2 O 2 / Kerosene LPRE Development of Low Cost Propulsion Systems for Launch- and In Space Applications Low Cost Propulsion Systems for Launch-, In Space- and Space Tourism Applications Seite 7; Space Propulsion 2016 / Rome

8 3.1 Development Strategy Low cost propulsion systems are (one) key component to realize low cost launch- and in space applications! How to achieve low cost propulsion? Simplified design of rocket engines and turbo pumps Moderate operational parameter (chamber pressure, temperature) Prefer industrial materials and matured manufacturing technologies instead of high-tech Prefer numbering-up instead of scale-up - Consider unification of propulsion system design for first and second launcher stages via clustering Environmentally benign and easy to handle propellant components - LOX resp. H 2 O 2, EtOH, LCH 4, Kerosene => avoid NO 2 / N 2 O 4 and hydrazine! Approach - Expandable engines: improve designs based on proven technologies (USA / USSR / Europe / Japan) - Reusable engines / turbo pumps: focus on (partially) ceramic systems Low Development Cost Propulsion of Low Systems Cost Propulsion for Launch-, Systems In Space- for Launch- and Space and In Tourism Space Applications Applications Dr.-Ing. Dr.-Ing. P. P. Weuta, Weuta, Dipl.-Ing. Dipl.-Ing. N. N. Jaschinski Jaschinski Space Seite 8; Propulsion / Rome

9 Development of Liquid Propellant Engines Seite Space 9; Propulsion / Rome

10 4. Development of Liquid Propellant Engines Technology demonstrator: Type 1 Development of expendable rocket engines: focus on metallic thrust chambers Process Parameter (35 kn SL) - Chamber pressure: 5 MPa - Propellant feed rate: ~ 14 kg / s (LOX + Ethanol) Design overview - Regenerative cooling - Use series production enabling technologies (welding / brazing) - Coaxial injector credit: J. Aurich (TU-Dresden 2015) Increase to higher thrust classes depending on market demand Seite Space 10; Propulsion / Rome

11 4.1 Development of Liquid Propellant Engines Technology demonstrator: Type 2 Development of re-usable rocket engines: focus on ceramic thrust chambers Ceramic thrust chambers are very promising candidates for multiple reusability - Low thermal expansion - System simplification cost reduction, high reliability - High specific strength at elevated temperatures - Oxidation resistance - Improved lifetime Design overview Thermo-shock resistance Thermal cycling ability - Use of highly effective transpirational cooling preferred - LOX + LCH 4 or Ethanol - Injector: coaxial type; use series production enabling technologies (welding / brazing) Process Parameter (35 kn SL) - Chamber pressure: 5 MPa Development of Low Cost Propulsion Systems for Launch- and In Space Applications Seite 11; Propellant feed rate: up to14 kg / s credit: DLR (M. Ortelt) Ref.: M. Ortelt Effusion cooled CMC rocket thrust chamber. 56 th International Astronautical Congress, Fukuoka, Japan.

12 4.2 Development of Liquid Propellant Engines Ceramic Thrust Chamber Commercial exploitation of ceramic technology intended: WEPA DLR joint evaluation of market potential in progress - long term experience with ceramic thrust chambers (DLR) Multiple successful tests with LOX / LH 2 (GH 2 ) Chamber pressures up to 100 bar / huge upside potential - Use of non-oxide and oxide ceramic matrix material (CMCs) Next steps: design / manufacturing of technology demonstrator engines using for LOX / LCH 4 and LOX / Ethanol credit: DLR (M. Ortelt) Ref.: M. Ortelt, H. Hald, A. Herbertz, I. Müller. 3 7 October Application potential of combined fibre reinforced technologies in rocket thrust chambers. 62 nd International Astronautical Congress, Cape Town, South Africa. credit: DLR (M. Ortelt) Seite Space 12; Propulsion / Rome Ref.: M. Ortelt, H. Hald, I. Müller Status and future perspectives of the CMC rocket thrust chamber development at DLR. 65 th International Astronautical Congress, Toronto, Canada.

13 Development of Turbo Pump Units Seite Space 13; Propulsion / Rome

14 5. Development of Turbo Pump Unit overview Technology demonstrator unit - Exit pressure: max. 75 bar - Max. 30,000 RPM; single shaft design - Open gas generator cycle (LOX / fuel) - Designed for reusability: focus on bearings Propellant systems: LOX / Ethanol and LOX / LCH 4 Mass flow rate: ~ kg/s (35 kn demonstrator engine) Weight: max. 25 kg (incl. gas generator + control unit) Arrangement: turbine fuel oxidizer Seite Space 14; Propulsion / Rome

15 5.1 Development of Turbo Pump Unit overview Turbine Pump Seals - single or double axial stage, impulse type - partial admission of drive gas - inlet temperature: < 850 K - single radial stage - dynamic type (majority) Bearings - ceramic material based Status journal type transpirational lubrication (collaboration with DLR and TU Kaiserslautern (Prof. Böhle)) credit: Wolter / Zetschke (TU-Dresden 2014) - First spinning tests of TPU to commence in Q (electric drive) Seite Space 15; Propulsion / Rome

16 5.2 Development of Turbo Pump Unit overview (aktualisierte Variante einfügen) credit: I. Matyash (TU-Dresden 2015) LOX Fuel Adaptation of technology demonstrator to requirements in H2020 / SMILE- project in progress (Small Innovative Launcher for Europe) Seite Space 16; Propulsion / Rome

17 H 2 O 2 -Concentration Technology Seite Space 17; Propulsion / Rome

18 6. Supply of H 2 O 2 (88-98 %): Motivation Advantages of H 2 O 2 -based propulsion systems - Storability / no evaporative losses during pre-operation time - Simplified, non cryogenic feed system (turbo pump and pressure feeding) - No chill down of system prior to ignition required - Reliable, hypergolic ignition process (catalytic decomposition) - Multiple burns possible - No safety / toxicity issues compared to N 2 O 4 / UDMH - Reduced system complexity => increased operational reliability! Use in many different propulsion systems possible - launchers, upper stages, sounding rockets, space planes, RCS Very high strength H 2 O 2 required for high performance systems - H 2 O 2 (95 %) / Kerosene does show comparable overall system performance with respect to LOX / Kerosene (=> higher density impulse of H 2 O 2 system) Limited commercial availability / high costs, even though one large company entered pilot production of 98 % - grade in late 2015 Seite Space 18; Propulsion / Rome

19 6.1 Supply of H 2 O 2 (88-98 %) H 2 O 2 concentration plant developed by WEPA-Technologies (EUcustomer / 2015) - Capacity: up to ~ 50 kg / d (91 %) - Feed: 50 % - 70 % H 2 O 2 - Fully automatic, 24 / 7 operability implementable - Working packages supplied by WEPA-Technologies Conceptional process design incl. safety concept Detail engineering (process-, control- and electrical diagrams) Equipment purchase Erection and commissioning Trouble shooting Very safe production process up to 98 % concentration available (~ 50 kg / day) - Scale-up to 1500 kg H 2 O 2 / day possible (set-up in ft container) Seite Space 19; Propulsion / Rome

20 6.2 Supply of H 2 O 2 (91 %) : Plant => general commercialisation of H 2 O 2 supply intended (88 98 %) => customer requests welcome! Control by PLC: LabVIEW RT (alternative: TWINCAT) Development of Low Cost Propulsion Systems for Launch- and In Space Applications Seite 20;

21 Summary Seite Space 21; Propulsion / Rome

22 7. Summary: development activities at WEPA-Technologies Liquid propellant rocket engines and turbo pump units - Focus on low cost and potential re-usability => ceramic materials: thrust chamber (transpiration cooling) resp. journal bearings - Present: 35 kn LPRE technology demonstrator (LOX / Ethanol and LOX / LCH 4 ) - Spinning tests of TPU (LOX / Ethanol) to commence in Q (electric drive) - Adaptation of technology demonstrator to requirements of H2020 / SMILE- project in progress (Small Innovative Launcher for Europe) H 2 O 2 - Significant facilitation of development and reliable operation of propulsion systems however: difficult supply situation at concentrations > 70 % - On-site concentration unit available to enable flexible project activities Key features Very safe production process up to 98 % concentration available fully automatic, 24 / 7 operability implementable reference plant available : ~ 50 kg / day capacity / 91 % H 2 O 2 - Production technology scalable up to ~ 1500 kg H 2 O 2 / day Development of Low Cost Propulsion Systems for Launch- and In Space Applications Seite 22; => customer requests welcome!

23 Thank you for your attention! Development of Low Cost Propulsion Systems for Launch- and In Space Applications Seite 23; Dr Ing. P. Weuta Pico- and Nano-Satellite Conference (09/2015) Dipl.- Ing. N. Jaschinski

24 Seite Space 24; Propulsion / Rome